Retractable system for aeronautical sensors

ABSTRACT

The invention discloses a retractable optical sensor ( 1 ) composed of an EO/IR (Electro-Optical/Infrared Remote) sensor ( 2 ) which is fastened to an articulated structure ( 3 ) that is actuated by an actuator ( 4 ); the structure ( 3 ) accomplishes angular movement whose turning point is located in an end that is mounted to an articulation support ( 5 ); the articulation support ( 5 ) is fastened to the support ( 6 ) which is fastened to the aircraft structure ( 7 ); the actuator ( 4 ) is electrically or hydraulically actuated and it has an end united to a support ( 8 ) which is fastened to the aircraft structure ( 7 ); the opposite end of the actuator ( 4 ) is articulated to the structure ( 3 ) and it promotes angular movement of the structure ( 3 ); the EO/IR sensor ( 2 ) presents a cylindrical shape having a spherical end; an articulated door ( 9 ) solidary to the movement of the structure ( 3 ) is mounted close to said spherical end; the movement of the door ( 9 ) is limited by the rods ( 10 ) for actuating the door, and the rods ( 10 ) are also fastened to the structure ( 3 ).

The present invention patent discloses a constructive form for aretractable system applied in aircraft, said system having a mechanismcontained in a protection compartment allowing retraction or expositionof a communication/navigation equipment, such as an optical-electronicsensor. The elucidated system presents a constructive disposition thatmakes possible to guarantee the integrity of the equipment, spendingless space for accommodation, low influence in the air flow passing bythe aircraft fuselage and, in consequence, low vibration of theequipment.

DESCRIPTION OF STATE OF ART

The aviation, either civilian or military, uses several electronicsystems, which are fundamental for communication activities, navigationand warning (surveillance), such as sensors, antennas and radar. Theoptical sensors allow the pilot identify specifically geographicalaccidents in low visibility environments. The electronic systems,depending on the purpose and dimensions of the equipments, are allocatedin the aircraft belly, disposed externally or in compartments having aspecific fairing, characterizing a protuberance on the smooth lines ofthe aircraft.

The inconveniences of such protuberances reside in the fact of anincrease in the aerodynamic drag, which influences the consumption offuel, range and speed limit of the aircraft directly, and also promotesturbulence. Further, generally speaking, the properly said sensorspresent a spherical shape in whose surface is located one or more lenseswith a circular format in plan. Once such sensors are exposed toairflow, they become susceptible to vibrations due detachment ofaerodynamic vortexes. It is also known, that useful life of the sensorsis related to the intensity of the vibrations which are proportional todynamic pressure and exposure of the sensors to the airflow.

Due the cost of such equipments and strategic importance inreconnaissance missions, the installation in aircraft is usually made ina way what the equipment is retractile, making possible its exposurewhen necessary and retraction when it is not in use.

Among the different types of known retractable systems, the most commonare those that execute vertical movement as taught by U.S. Pat. No.3,982,250, U.S. Pat No. 3,656,164, U.S. Pat. No. 4,593,288, U.S. Pat.No. 5,969,686, U.S. Pat. No. 5,918,834. However, such a verticalmovement implicates in interfaces with the pressurized area of theaircraft or in generation of great protuberances on the exterior side ofthe fuselage and, consequently, the inconveniences above mentioned.

In other exposition/retraction pantographic systems also known, theoperation kinematics is seen as a complex procedure mainly due tointeraction with the articulated doors, which are defined by heavymechanisms having big physical dimensions responsible for maintainingthe compartment closed. This is because their surfaces generatedisturbances in the air flow when they are extended during the flight,so that the whole assemblage becomes subject to strong vibrations whichcause, along the time, mechanical wearing for the parts composing thesystem and damage to the sensors.

It is noticed that the previous state of art is replete ofinconveniences that induce to high costs of operation and maintenance.Thus, the present invention discloses a new technique that suppressessuch inconveniences, as well as it provides a smooth curvilinear surfacethat reduces turbulence and drag.

SUMMARY OF THE INVENTION

The objective of the present invention is to present a retractablesystem for aeronautical sensors which is capable to guarantee physicalintegrity of the equipment.

Another objective of the present invention is to present a retractablesystem for aeronautical sensors that makes possible exposition andretraction of the electronic equipment starting from a short angularmovement.

Another objective of the present invention is to present a retractablesystem for aeronautical sensors that uses just a single door built in afairing of the aircraft.

Another objective of the present invention is to present a retractablesystem for aeronautical sensors which doesn't require exaggeratingprotuberances on the aircraft fuselage or wing, thus allowing a minimalspace for accommodation inside the aircraft.

BRIEF DESCRIPTION OF DRAWINGS

The present invention will be briefly described based in an embodimentexample represented by the drawings. The figures show:

FIG. 1—a schematic perspective view of an aircraft having a sensoraccording to previous state of art;

FIG. 1 b—a schematic perspective view of an infrared optical sensor inan exposed position.

FIG. 2—a side view of the retractable system for aeronautical sensors,in a retracted position;

FIG. 3—a side view of the retractable system for aeronautical sensors,in a position of exposition of the sensor.

FIG. 4—a second side view of the retractable system for aeronauticalsensors, in a position of retraction of the sensor.

FIG. 5—a lower view of the retractable system for aeronautical sensors,in a position of exposition of the sensor.

DETAILED DESCRIPTION OF THE INVENTION

The present invention solves the inconveniences of the previous state ofart, through a sensor disposed in an articulated structure, which ismovable through an actuator. There is a door, solidary to the sensor,fitted to the channel through a place where the sensor is exposed, sothat the movement of the door and of the sensor is reduced, minimizingthe adjustment and loosen spaces problems.

FIG. 1 presents a schematic perspective view of an aircraft having asensor, according to previous state of art, wherein it is noticed anarea with bulbous shape located on the lower portion of the fuselage.

In FIG. 1 b it is illustrated in details the sensor in exposed positionaccording to previous state of art. In this representation, theexposition and retraction system doesn't have means that can impede thepassage of air to the interior of the fuselage.

In the FIG. 2 it is exhibited the duramen of the present invention, theretractable system 1 being composed by an infrared optical sensor 2 orsimply EO/IR (Electro-Optical/Infrared Remote) which is assembled to astructure 3 having a substantially trapezoidal profile which isarticulated according to the action of an actuator device 4.

The structure 3 accomplishes angular movement whose turning point islocated in an end mounted respectively on a bearing or articulationsupport 5. The articulation support 5 is fastened to the support 6 thatis perpendicularly fastened in the face of the aircraft structure 7.

The actuator 4 can be electrically or hydraulically actuated and itpresents one of its ends united to a support 8 that is fastened to theaircraft structure 7. The opposite end of the actuator 4, specificallythe extremity of the piston, is articulated in relation to the structure3 and it promotes the angular movement of said structure.

An articulated door 9 solidary to the movement of the structure 3 ismounted close to the internal wall of the fairing that protects thesystem. The movement of said door is limited by a pair of rods 10 thatinterconnect the articulation points of the hinges with the points ofthe structure 3.

The door 9 is defined by a substantially curved sheet fitting inpractically half of the contour of the circular surface of said sensor2.

From the condition showed in FIG. 2 to the condition presented in FIG.3, basically, the kinematics of exposition of the retractable opticalsensor is comprised by the action of the actuator 4, which upon pushingthe piston promotes a simultaneous angular movement of the structure 3,door 9 and EO/IR 2. Such a movement makes the EO/IR sensor 2 to bepositioned beyond the surface of the fairing 11, giving it operationconditions. In this condition, the EO/IR sensor 2 fills in integrally anopening in the fairing 11, thus impeding that the air flow generatesimproper vibrations to the other components comprising the retractablesystem 1.

The retraction of the mechanism, according to FIG. 2, is provided againby the actuator 4, which when pulling the piston rotates the structure3, door 9 and EO/IR sensor 2. In this condition, the door 9 isresponsible for obstructing the existent openings between the EO/IRsensor 2 and the opening of the fairing 11.

From the description above it is evident that the advantage of thepresent invention resides in the fact of providing a retractable system1 capable of exposing and retracting the infrared optical sensor withoutthe need of actuator devices and doors assembly demanding to beconditioned in voluminous protection fairings.

A small portion of the semi-spherical or ogival end of the sensor 2 ismaintained projected outside of the fairing. However, the influence ofsuch protuberance in the generation of drag is minimal.

These advantages are of relevant importance from the economical andstrategic point of view, because besides increasing the useful life ofthe infrared optical sensor 2 and of the whole equipment, they alsoallow a best performance of the aircraft during the execution of itsmissions.

It was described an example of favourite materialization of theinvention, and it should be understood that the scope of the presentinvention includes other possible variations, such as employment ofseveral types of radar and/or antennas, and it is only limited by thetenor of the attached claims, comprising its possible equivalents.

1) “RETRACTABLE SYSTEM FOR AERONAUTICAL SENSORS”, wherein it comprises aretractable mechanism (1) composed of a communication/navigationequipment (2) which is fastened to an articulated structure (3) actuatedby an actuator (4). 2) “RETRACTABLE SYSTEM FOR AERONAUTICAL SENSORS”,according to claim 1, wherein the communication/navigation equipment (2)is defined by an infrared optical sensor. 3) “RETRACTABLE SYSTEM FORAERONAUTICAL SENSORS”, according to claim 1, wherein the structure (3)accomplishes an angular movement whose turning point is located in anend that is mounted to an articulation support (5). 4) “RETRACTABLESYSTEM FOR AERONAUTICAL SENSORS”, according to claim 1, wherein thearticulation support (5) is fastened to the support (6) which isfastened to the aircraft structure (7). 5) “RETRACTABLE SYSTEM FORAERONAUTICAL SENSORS”, according to claim 1, wherein the actuator (4)has an end united to a support (8) which is fastened to the aircraftstructure (7); the opposite end of the actuator (4) is articulated tothe structure (3). 6) “RETRACTABLE SYSTEM FOR AERONAUTICAL SENSORS”,according to claim 1, wherein the actuator (4) is electrically orhydraulically actuated and it promotes angular movement of the structure(3). 7) “RETRACTABLE SYSTEM FOR AERONAUTICAL SENSORS”, according toclaim 1, wherein the optical sensor (2) presents a cylindrical shapehaving a spherical end. 8) “RETRACTABLE SYSTEM FOR AERONAUTICALSENSORS”, according to claim 1, wherein an articulated door (9) solidaryto the movement of the structure (3) is mounted close to the internalwall of the fairing of the protection compartment. 9) “RETRACTABLESYSTEM FOR AERONAUTICAL SENSORS”, according to claim 1, wherein thearticulation points of the hinges with the points of the structure (3)are interlinked by a pair of rods (10). 10) “RETRACTABLE SYSTEM FORAERONAUTICAL SENSORS”, according to claim 1, wherein the door (9) isdefined by a substantially curved sheet fitting in practically half ofthe contour of the circular surface of said sensor (2). 11) “RETRACTABLESYSTEM FOR AERONAUTICAL SENSORS”, according to claim 1, wherein thecommunication/navigation equipment (2) is a radar and/or antenna.